Shape design sensitivity analysis of 2D anisotropic structures using the boundary element method

2004

Thin-Walled Structures

Composite cylindrical shells and panels are widely used in aerospace structures. These are often subjected to defects and damage from both in-service and manufacturing events.Delamination is the most important of these defects. This paper deals with the computational modelling of delamination buckling and postbuckling of laminated composite cylindrical shells subjected to external pressure. The use of three-dimensional finite elements for predicting the delamination buckling and postbuckling of these structures is computationally expensive. Here the combined double-layer and single-layer

mentioning

confidence: 99%

Delamination buckling and postbuckling in composite cylindrical shells under external pressure

2004

Thin-Walled Structures

“…The derivatives of the kernels for anisotropic materials will be as follows [17]: Defining the real functions  j ,  j as,…”

Section: Vmentioning

confidence: 99%

“…[17], a directly differentiated form of the BIE, with respect to boundary point coordinates, was used to calculate stress and displacement derivatives for 2D anisotropic structures. In Ref.…”

Section: Introductionmentioning

confidence: 99%

Fracture Mechanics Analysis of Composite Structures Using the Boundary Element Shape Sensitivities

2009

AIAA Journal

“…& Oswald, T. Feb. 2003 In : International Journal of Pressure Vessels and Piping. 80,1, similar to the method employed in Ref. [21].…”

Section: Verification Of the Localmentioning

confidence: 99%

“…The phenomenon of progressive failure in laminated composite structures is yet to be understood, and as a result, reliable strategies for designing optimal laminated composite structures for desired life and strength are not yet available [1] For the past two decades analytical and numerical analysis have been carried out by many researchers [2][3][4][5][6][7][8][9][10][11][12][13][14] to analyse delaminated composite structures, considering their buckling and post-buckling behaviour. The early work belongs to Chai et al [2] who characterized the delamination buckling models by the delamination thickness and number of delaminations through the laminate thickness.…”

Section: Introductionmentioning

confidence: 99%

Global buckling behaviour and local damage propagation in composite plates with embedded delaminations

International Journal of Pressure Vessels and Piping

Oswald

2003

Finite element models were developed to study global, local and mixed mode buckling behaviour of composite plates with embedded delaminations under compression. The global modelling results were compared with corresponding experimental results. It is shown that the numerical results for embedded delaminations agree very well with the experimental results, whereas the difference between the results was high for delaminations located at the edge of the plates. It is also shown that at lower loading levels the interaction of global and local buckling is negligible. At higher loading levels the strain energy release rate distribution and the delamination growth potential at the delamination front strongly depend on the shape of the debonded region and the local buckling mode. It was observed that the local buckling mode was highly influenced by the laminate stacking sequence. In the course of global buckling a parametric study was carried out to investigate the influence of the delamination size, shape and alignment of a series of composite plates.